Drag reduction analysis of wing airfoil E562 with forward wingtip fence at cant angle variations of 75° and 90

• Main Authors: P., Setyo Hariyadi S., Sutardi, Widodo, Wawan Aries
• Format: Conference Proceeding
• Language: English
• Subjects: Aerodynamics; Angle of attack; Computational fluid dynamics; Computer simulation; Downwash; Drag reduction; Flow velocity; Fluid flow; High lift; Induced drag; Mathematical models; Vortices; Wing tip vortices
• ISSN: 0094-243X; 1551-7616
• DOI: 10.1063/1.5049994

Airfoil modeling is very important especially in determining the airfoil’s performance. One very important in the airfoil design is how to make airfoil with high lift and low drag to obtain a large lift to drag ratio. In this study, the design was carried out with Eppler 562 wing airfoil by adding an endplate at the end of the wing. Endplate used in the form of forward wingtip fence. The addition of endplate at the tip of the wing aims to reduce the occurrence of tip vortex. The emergence of a tip vortex is due to the flow from the lower surface to the upper surface. These tip vortex can cause induced downwash velocities and reduce effective angle of attack. This research is conducted by numerical simulation using simulation software with turbulent model k-ω SST. Freestream flow rate to be used is 10 m/s with angle of attack (α) = 0°, 2°, 4°, 6°, 8°, 10°,12° 15°, 17° and 19°. On forward wingtip fence cant angel 90° produce higher performance than other wing start at α = 6° while forward wingtip fence cant angel 75°.produce better performance at α = 19°. The tip vortices formed by the winglet produce very different shapes to each other and it appears to be a significant effect of the flow field above the wing surface. These vortices will change shape when the angle of attack of the model is changed. The values of the vortices behind the winglet are also different which indicate the effect of induced drag.